KR102011484B1 - Oxidizer supplying unit for rocket and rupture member of oxidizer supplying unit - Google Patents

Abstract

The present invention relates to the control of the oxidant supply unit only by controlling the ignition unit, and thus relates to an oxidant supply unit for the rocket device and a rupture member of the oxidant supply unit for controlling the transfer of the oxidant between the oxidant capsule and the solid fuel.
The oxidant supply unit for the rocket device is an oxidant supply unit for connecting the oxidant capsule in which the oxidant is stored and the solid fuel so that the oxidant is supplied to the solid fuel, wherein the oxidant supply unit forms a discharge path of the oxidant. A supply body having an exposed hole formed therebetween and disposed between the oxidant capsule and the solid fuel; A rupture member that blocks the oxidant from being delivered to the solid fuel and closes the exposed hole so as to be decomposable by flame or heat; And a piercing hole formed to penetrate the communication hole part corresponding to the exposed hole part to form a discharge path of the oxidant, and laminated on the rupture member to face the oxidant capsule.

Description

OXIDIZER SUPPLYING UNIT FOR ROCKET AND RUPTURE MEMBER OF OXIDIZER SUPPLYING UNIT}

The present invention relates to an oxidant supply unit and a rupture member of the oxidant supply unit for the rocket device, and more specifically, it is possible to control the oxidant supply unit only by controlling the ignition unit, thereby transferring the oxidant between the oxidant capsule and the solid fuel. It relates to an oxidant supply unit and a rupture member of the oxidant supply unit for the rocket device for controlling the.

In general, hybrid rockets use solid fuels and liquid oxidants to provide propulsion. As the solid fuel, a polymer called plastic may be used, and as the oxidizing agent, liquid nitrous oxide (LN 2 O), liquid oxygen (LOx), or the like may be used.

The oxidant is stored in a pressurized tank.

The solid fuel is located on the inner wall of the hollow, generally tubular combustion chamber housing. In addition, solid fuel extends from the rear of the pressurized tank to the throat and nozzles.

The ignition device (flash type or flame type) initiates combustion, and the valve provided between the oxidant and the solid fuel can supply the oxidant to the solid fuel through cooperative control with the ignition device.

However, since the rocket according to the related art can control the valve together with the control of the ignition device to start stable combustion in the combustion chamber housing, the control operation for combustion becomes complicated, and the size of the rocket increases due to the configuration of the valve. This can lead to incomplete combustion due to control errors.

Republic of Korea Patent Publication No. 10-0730607 (Invention name: Integrated hybrid rocket system, 2007. 06. 20. notification)

An object of the present invention is to solve the conventional problems, it is possible to control the oxidant supply unit only by the control of the ignition unit, thus oxidant supply unit for the rocket device for controlling the transfer of the oxidant between the oxidant capsule and the solid fuel The present invention provides a burst member of an oxidant supply unit.

In addition, an object of the present invention is to control the delivery of the oxidant between the oxidant capsule and the solid fuel, it is possible to replace the function of the valve provided in the oxidant supply unit, since the additional components necessary for the control of the valve and the valve is omitted Of the oxidizer supply unit and oxidant supply unit for the rocket unit to reduce the load and size of the rocket unit, simplify the control operation for the combustion of solid fuel, and improve the propulsion of the rocket unit in response to the reduced load and size. In providing a burst member.

According to a preferred embodiment for achieving the above object of the present invention, the oxidant supply unit for a rocket device according to the present invention is an oxidant supply for connecting the oxidant capsule and the solid fuel is stored so that the oxidant is supplied to the solid fuel In the unit, the oxidant supply unit, the supply body is formed through the exposed hole forming the discharge path of the oxidant, the supply body disposed between the oxidant capsule and the solid fuel; A rupture member that blocks the oxidant from being delivered to the solid fuel and closes the exposed hole so as to be decomposable by flame or heat; And a piercing hole formed to penetrate the communication hole part corresponding to the exposed hole part to form a discharge path of the oxidant, and laminated on the rupture member to face the oxidant capsule.

Here, the supply body, the seating hole portion is inserted into the injection portion of the oxidant capsule; And a cardboard jaw portion provided in the seating hole for mounting the rupture member.

The piercing may include a piercing plate portion formed through the communication hole portion and laminated on the rupture member; And a hollow communication tube portion protruding from the piercing plate portion to communicate with the communication hole portion.

The rupture member of the oxidant supply unit according to the present invention is a rupture member provided in the oxidant supply unit for supporting the oxidant capsule in which the oxidant is stored. The oxidant is blocked from being delivered to the solid fuel and can be decomposed by flame or heat.

Here, the bursting member includes a curvature having a groove having an arc-shaped inner cross section.

인 관계식이 성립된다.Here, the minimum thickness (mm) of the curvature portion is t, the pressure (MPa) of the oxidant acting on the curvature portion is P, the inner diameter (mm) of the curvature portion is D, and the ellipsoid of the curvature portion is When the shape factor is A and the yield stress MPa of the curvature is S,

Relation is established.

Here, the bursting member includes a celluloid material.

Here, the rupture member, the ignition (ignition) temperature of more than 200 degrees Celsius; Mechanical strength to withstand pressures up to 1000 psi at 100 degrees Fahrenheit; And a decomposition rate of 2 mm / s or more upon decomposition by flame or heat; At least one of them.

According to the oxidant supply unit for the rocket device and the rupture member of the oxidant supply unit according to the present invention, it is possible to control the oxidant supply unit only by controlling the ignition unit, thereby controlling the transfer of the oxidant between the oxidant capsule and the solid fuel. have.

In addition, the present invention, in controlling the transfer of the oxidant between the oxidant capsule and the solid fuel, can replace the function of the valve provided in the oxidant supply unit, the additional components required for the control of the valve and the valve is omitted, the rocket It is possible to reduce the load and size of the device, to simplify the control operation for the combustion of solid fuel, and to improve the propulsion of the rocket system in response to the reduced load and size.

In addition, the present invention can stabilize the stacking coupling of the rupture member and the piercing and sealing ring in the supply body, simplify the arrangement and coupling between the supply body and the oxidant capsule, and facilitate the positioning of the oxidant capsule in the supply body.

In addition, the present invention facilitates the breakage of the fracture member by the coupling force of the supply body and the oxidant capsule, the inlet opening of the oxidant capsule is easy, it is possible to prevent the leakage of the oxidant.

In addition, the present invention can prevent deformation and breakage due to direct contact with the oxidant through the rupture member, and can withstand the pressure of the oxidant discharged from the inlet of the oxidant capsule.

In addition, the present invention may have a mechanical strength that exceeds the discharge pressure of the oxidizing agent changes according to the external temperature through the rupture member.

In addition, the present invention can increase the retraction rate, improve the propulsion performance, and increase the combustion efficiency through the swirl flow according to the combustion in the solid fuel.

In addition, the present invention can simplify the manufacture and coupling of the ignition unit, it is possible to stabilize the coupling of the ignition unit and the solid fuel.

In addition, the present invention can store the oxidant capsule separately, simplify the opening of the oxidant capsule in the process of assembling the oxidant capsule in the robot device, it is possible to prevent the leakage of the oxidant.

In addition, the present invention implements the modularization of the rocket device through the combustor housing, as well as the individual components are closely coupled to each other through the modular rocket device, such as a water rocket or air rocket while realizing a combustion phenomenon similar to the actual rocket Safety can be secured.

In addition, the present invention can prevent the flow of components in the combustor housing through the gaskets, and can improve the adhesion between the components.

In addition, the present invention can amplify the thrust force through the nozzle, and shields between the discharged combustion material and the combustor housing, it is possible to improve the coupling force between the nozzle and the combustor housing.

In addition, the present invention can stabilize the flight of the rocket housing through the rocket housing.

In addition, since the solid fuel and the oxidant are separated and stored even after the assembly of the rocket device, there is no risk of explosion, thereby ensuring high safety, and the combustion phenomenon and the internal structure can be simulated similarly to the actual rocket.

In addition, the present invention is because the fumes and operation sounds generated during combustion are similar to the flight phenomena of the actual rocket, it is possible to use in everyday life, such as learning materials for educational field, props for leisure activities, and various applications Can be represented.

In addition, the present invention can be utilized as an optimal educational rocket model or leisure rocket model through the best safety.

1 is a view showing a bursting rocket device according to an embodiment of the present invention.
Figure 2 is an exploded view showing a combustor module in a ruptured rocket device according to an embodiment of the present invention.
3 is an exploded view showing an oxidant supply unit in a ruptured rocket device according to an embodiment of the present invention.
4 is a cross-sectional view illustrating a rupture member of the oxidant supply unit shown in FIG. 3.
5 is a cross-sectional view showing a state before assembly of the oxidant capsule and the oxidant supply unit in the bursting rocket device according to an embodiment of the present invention.
6 is a cross-sectional view showing a state after assembly of an oxidant capsule and an oxidant supply unit in a ruptured rocket device according to an embodiment of the present invention.

Hereinafter, with reference to the accompanying drawings will be described an embodiment of the oxidant supply unit for the rocket device and the rupture member of the oxidant supply unit according to the present invention. At this time, the present invention is not limited or limited by the embodiment. In addition, in describing the present invention, a detailed description of known functions or configurations may be omitted to clarify the gist of the present invention.

The oxidant supply unit and the rupture member of the oxidant supply unit for the rocket device according to the present invention will be described as being applied to the bursting rocket device according to an embodiment of the present invention with reference to FIGS.

The bursting rocket device according to an embodiment of the present invention includes a solid fuel 10, an ignition unit 20, an oxidant capsule 30, and an oxidant supply unit 40. In addition, the bursting rocket device according to an embodiment of the present invention may further include at least one of a combustor housing 50, a nozzle 60, a rocket housing 70, and a dummy unit 80. .

Solid fuel 10 provides propulsion by combustion.

The solid fuel 10 has a pushing hole 11 formed in the longitudinal direction thereof. For example, the solid fuel 10 may have a hollow tubular shape according to the formation of the propulsion hole 11. The solid fuel 10 may be provided with one or more as necessary, without limiting the number of the propulsion holes 11. Although not shown, a spiral groove may be formed in the inner wall of the propulsion hole 11 to induce a swirl flow of the material passing through the propulsion hole 11.

One end of the solid fuel 10 is provided with a first supporting jaw portion 12 for close support with the nozzle 60, and the other end of the solid fuel 10 is in close contact with the oxidant supply unit 40 The second support jaw portion 13 may be provided. The first supporting jaw portion 12 and the second supporting jaw portion 13 may be recessed at the end edges of the solid fuel 10, respectively. Then, the first gasket 15 is coupled to the first support jaw 12 to improve adhesion to the nozzle 60, and the second gasket 16 is coupled to the second support jaw 13 to provide the oxidant supply unit. Adhesion with 40 can be improved.

An end portion of the solid fuel 10 may be provided with an ignition unit seat 14 for mounting the ignition unit 20. The ignition unit seat 14 may be recessed at the end of the solid fuel 10 so that the ignition agent body 21 or the ignition agent 22 of the ignition unit 20 may be inserted and seated.

The ignition unit 20 is coupled to the solid fuel 10. The ignition unit 20 generates a flame or heat.

The ignition unit 20 includes an ignition agent body 21 coupled to the solid fuel 10, an ignition agent 22 inserted into the ignition agent body 21 to generate a flame or heat, and an ignition agent 22. It may include an ignition line 23 for applying a flame or heat to the. The ignition unit 20 may omit the ignition body 21 as necessary.

The ignition agent body 21 may be manufactured through a three-dimensional printing process, but is not limited thereto, and may use various known ignition agents bodies.

The ignition agent 22 may be made of a mixture of sorbitol (or sugar) and potassium nitrate (KNO 3), but is not limited thereto, and may be utilized through various known ignition agents.

The ignition wire 23 may include a nichrome wire that is generated by an applied power source, but is not limited thereto, and may use various known ignition wires. The ignition wire 23 may be disposed through the propulsion hole 11.

Looking at the manufacturing method of the ignition unit 20 described above, the manufacturing method of the ignition unit 20 may include a mixing step, the melting step, the filling step, the ignition wire connection step, the curing step.

In the mixing step, sorbitol (or sugar) and potassium nitrate (KNO 3), which are raw materials of the ignition agent 22, are pulverized into particles having a predetermined size, and mixed at a predetermined weight ratio to prepare an ignition mixture.

The melting step melts the ignition agent mixture in a heating furnace at a predetermined temperature. In the melting step, the ignition agent mixture may be gradually melted in a plate-shaped furnace to prevent safety accidents.

The filling step fills the ignition agent mixture in the ignition agent body.

The ignition wire connection step partially immerses the ignition wire in the ignition agent mixture which has been filled.

The curing step cures the ignition agent mixture in the molten state in the ignition agent body 21. At this time, the curing step may represent a state in which the ignition wire 23 is immersed.

Here, after the filling step after the curing step, a part of the ignition wire 23 can be connected to the cured ignition agent mixture through the ignition agent connection step.

The oxidant capsule 30 stores the oxidant supplied to the solid fuel 10. The corner portion of the oxidant capsule 30 is rounded so as to withstand the pressure of the stored oxidant sufficiently.

The oxidant capsule 30 may include a capsule part 33 in which an oxidant is stored, and an injection part 31 extending from the capsule part 33 to form an inlet 32 through which the oxidant is discharged.

Here, the inlet 32 of the oxidant capsule 30 is closed by the breaking member 34 to prevent the discharge of the oxidant. The breaking member 34 is broken by the bonding force between the oxidant capsule 30 and the oxidant supply unit 40, so that the inlet 32 of the oxidant capsule 30 is opened, and the oxidant is discharged through the inlet 32. To help. The coupling force between the oxidant capsule 30 and the oxidant supply unit 40 may include a pressing force of the oxidant capsule 30 toward the solid fuel 10.

Although not shown, the break member 34 may have a groove having an arc-shaped cross section at the inlet 32. In other words, the breaking member 34 may form a convex or concave inner surface from the inlet 32 toward the solid fuel 10. Then, the breaking member 34 can withstand the discharge pressure of the oxidant sufficiently and can be prevented from being damaged by the discharge pressure of the oxidant.

When the breaking member 34 forms a convex inner surface, the breakage due to the bonding force between the oxidant capsule 30 and the oxidizing agent supply unit 40 can be facilitated, and the breaking member 34 forms a concave inner surface. In addition, the breaking member 34 may be prevented from being damaged by an external force other than the bonding force between the oxidant capsule 30 and the oxidant supply unit 40.

The oxidant capsule 30 may be provided with a support gasket 35. The support gasket 35 may surround the oxidant capsule 30 and prevent the oxidant capsule 30 from flowing in combination with the combustor housing 50.

The oxidant supply unit 40 connects the solid fuel 10 and the oxidant capsule 30. The oxidant supply unit 40 may adjust the amount of oxidant supplied to the solid fuel 10. The oxidant supply unit 40 may include a rupture member 42 for blocking the transmission of the oxidant toward the solid fuel 10. The bursting member 42 is decomposed by sparks or heat generated from the ignition unit 20. By disassembling the rupture member 42, the oxidant supply unit 40 may deliver the oxidant to the solid fuel 10.

The oxidant supply unit 40 is a supply body 41 disposed between the oxidant capsule 30 and the solid fuel 10, and the rupture that can be decomposed by the flame or heat while preventing the oxidant from being transferred to the solid fuel 10. The member 42 and a communication hole 432 forming a discharge path of the oxidant may be formed therethrough, and may include a piercing 43 stacked on the rupture member 42 to face the oxidant capsule 30. In addition, the oxidant supply unit 40 may further include a sealing ring 44 for sealing between the oxidant capsule 30 and the piercing 43.

The supply body 41 has a seating hole 411 into which the injection portion 31 of the oxidant capsule 30 is inserted, and a cardboard jaw portion 412 provided in the seating hole 411 for mounting the rupture member 42. May be included. The cardboard jaw portion 412 may protrude from the inner wall of the seating hole 411.

The seating hole 411 is a diameter corresponding to the diameter of the rupture member 42 and the piercing 43, and can suppress or prevent the flow of the rupture member 42 and the piercing 43 in the seating hole 411. For example, the inner diameter of the mounting hole 411 is substantially the same as the outer diameter of the rupture member 42 and the piercing 43, or corresponding to the allowable clearance than the outer diameter of the rupture member 42 and the piercing 43. It can be formed large.

The cardboard jaw portion 412 is provided in the seat hole 411 in a ring shape. The cardboard jaw portion 412 prevents the rupture member 42 and the piercing 43 from escaping toward the solid fuel 10, and when the oxidant capsule 30 is coupled to the supply body 41, the oxidant capsule 30 ) And the binding force between the oxidant supply unit 40 (the supply body 41 or the piercing 43) can be sufficiently acted, and the sealing between the oxidant capsule 30 and the piercing 43 can be stabilized.

The supply body 41 may have a through hole 413 through which an oxidant discharge path is formed. The exposure hole 413 is formed through the supply body 41 in accordance with the formation of the cardboard jaw portion 412, so as to communicate with the seating hole 411.

The bursting member 42 may be inserted into the seating hole 411 according to the coupling with the supply body 41, and may close the exposure hole 413. The rupture member 42 may include a celluloid material in the polymer compound, thereby stabilizing decomposition by flame or heat. More specifically, the bursting member 42 satisfies the discharge pressure of the oxidant by satisfying at least one of the ignition (ignition) temperature, the mechanical strength and the decomposition rate, and is stable by the flame or heat by the ignition unit 20. Decomposition takes place, and the oxidant is supplied to the solid fuel 10 stably.

The bursting member 42 may be crimped and supported between the piercing 43 and the supply body 41 and between the piercing 43 and the cardboard jaw portion 412 to prevent leakage of the oxidant.

To this end, the ignition (ignition) temperature of the rupture member 42 should be 200 degrees Celsius or more, the mechanical strength of the rupture member 42 must withstand pressure up to 1000 psi at a maximum of 100 degrees Fahrenheit, The rate of decomposition should be at least 2 mm / s for decomposition by flame or heat.

When the condition of the bursting member 42 is not satisfied, the bursting member 42 does not endure the discharge pressure of the oxidizing agent, so that there is a risk of breakage due to the discharge pressure of the oxidizing agent. When delivered to the solid fuel, problems such as incomplete combustion or poor ignition of the solid fuel 10 may occur due to an abnormal discharge phenomenon of the oxidant, such as excessive discharge of the oxidant or insufficient discharge of the oxidant.

The bursting member 42 may include a curvature 421 in which a groove having an inner cross section having an arc shape is recessed. In other words, the rupture member 42 may have a convex or concave inner surface toward the solid fuel 10 at the exposed hole 413. Then, the bursting member 42 can withstand the discharge pressure of the oxidant sufficiently and can be prevented from being damaged by the discharge pressure of the oxidant.

When the rupture member 42 forms a convex inner surface, the rupture member 42 facilitates disassembly by the ignition unit 20 due to its proximity to the solid fuel 10, and the rupture member 42 has a concave inner surface. When forming, the bursting member 42 can be prevented from being damaged by an external force.

For the curvature 421, the following relation must be established for stability against oxidant discharge pressure and stable resolution by flame or heat.

More specifically, the minimum thickness (mm) of the curvature 421 is t, the pressure of the oxidant acting on the curvature 421 (MPa) is called P, and the internal diameter (mm) of the curvature 421 is If D, the ellipsoidal shape coefficient of the curvature 421 is A, and the yield stress MPa of the curvature 421 is S,

인 관계식이 성립되는 것이다.

Relationship is established.

The pressure of the oxidant acting on the curvature 421 may be replaced by the oxidant discharge pressure discharged from the inlet of the oxidant capsule 30.

The bursting member 42 may further include a catching part 422 provided at the edge of the curvature 421. The locking portion 422 is formed in a ring shape at the edge of the curvature 421, so that it is securely stacked and supported on the cardboard jaw portion 412.

The piercing 43 has a piercing plate portion 431 through which the communication hole 432 is formed and stacked in the rupture member 42, and a hollow communication tube portion protruding from the piercing plate portion 431 so as to communicate with the communication hole 432. 433. The communication hole 432 may be formed to penetrate in correspondence with the exposure hole 413.

The piercing 43 may compress the rupture member 42 by the bonding force between the oxidant capsule 30 and the oxidant supply unit 40 to prevent leakage of the oxidant.

The sealing ring 44 is provided between the oxidant capsule 30 and the piercing 43 and is elastically deformable by the pressing force of the oxidant capsule 30 toward the solid fuel 10.

The combustor housing 50 includes a solid fuel 10, an ignition unit 20, an oxidant capsule 30, and an oxidant supply unit 40. As the combustor housing 50 is further included, it is possible to modularize the main components of the rocket unit and simplify the manufacture of the rocket unit.

The combustor housing 50 is coupled to one side of the combustor body 51 and the combustor body 51 in which the solid fuel 10, the ignition unit 20, the oxidant capsule 30, and the oxidant supply unit 40 are embedded. The first closing cap 52 closing one side of the combustor body 51 to expose the solid fuel 10 or the nozzle 60 to be added, and the oxidant capsule 30 is coupled to the other side of the combustor body 51. It may include a second closing cap 53 for supporting.

The combustor body 51 shows a hollow tubular shape for the interior of the components. The combustor body 51 may have a screw thread formed on one outer surface thereof for screwing with the first closing cap 52, and a screw thread formed on the other inner surface for screwing with the second closing cap 53.

A support rib is formed on the outside of the combustor body 51 to stabilize the coupling with the rocket housing 70 and prevent the flow in the rocket housing 70. Support ribs may be provided on both sides of the combustor body 51, as shown in FIG.

The components embedded in the combustor body 51 are stably supported inside the combustor body 51 by the first gasket 15, the second gasket 16, and the support gasket 35, and the combustor body 51. Prevents the flow of components.

In the first closing cap 52, a pressure discharge hole 521 for exposing the solid fuel 10 or the additional nozzle 60 may be formed therethrough. The pressure discharge hole 521 allows the flame or heat to be discharged at a pressure corresponding to the discharge of the oxidant. The first closing cap 52 is formed with a screw thread to ensure a stable screw coupling to one side of the combustor body (51).

The second closing cap 53 is formed with a screw thread so that a stable screw coupling is made to the other side of the combustor body 51. Although not shown, a support ring (not shown) is provided on the outer surface of the second closing cap 53 to stabilize the coupling with the rocket housing 70, and that the combustor housing 50 flows in the rocket housing 70. It can prevent. Although not shown, the second closing cap 53 is provided with a support cushion (not shown) to prevent deformation or breakage of the oxidant capsule 30 when the second closing cap 53 is coupled to the combustor body 51. can do. It is sufficient that the support cushion (not shown) can be disposed between the second closure cap 53 and the oxidant capsule 30.

For example, the second closing cap 53 supports the oxidant capsule 30 as it is coupled to the combustor body 51 to prevent the oxidant capsule 30 from flowing in the combustor housing 50 and at the same time the oxidant capsule ( 30) may provide a bonding force between the oxidant supply unit 40. In other words, when the first coupling cap 52 is coupled to the combustor body 51 and the degree of screwing between the second closing cap 53 and the combustor body 51 is adjusted, the oxidant capsule 30 By pressing the oxidant capsule 30 toward the solid fuel 10 toward the solid fuel 10, the fracture member 34 may be damaged as shown in FIG. 6.

As another example, the combustor housing 50 may further include a capsule pressurizing member 54 to provide a coupling force between the oxidant capsule 30 and the oxidant supply unit 40. Here, the second closing cap 53 supports the oxidant capsule 30 according to the combination with the combustor body 51 to prevent the oxidant capsule 30 from flowing in the combustor housing 50. Capsule pressing member 54 is coupled to the second closing cap 53 so as to reciprocate. The capsule pressing member 54 may be screwed to penetrate the second closing cap 53. Then, in the state in which the first closing cap 52 and the second closing cap 53 are respectively coupled to the combustor body 51, the degree of screwing between the capsule pressing member 54 and the second closing cap 53 is adjusted. When the oxidant capsule 30 is pressed toward the solid fuel 10, the oxidant capsule 30 pressurizing pressure is generated toward the solid fuel 10, thereby breaking the breaking member 34 as shown in FIG. 6. .

The nozzle 60 amplifies the propulsion force when the oxidant is delivered to the solid fuel 10. The nozzle 60 may amplify the driving force by amplifying the discharge pressure when the flame or heat is discharged to the outside of the combustor housing 50 at the pressure according to the discharge of the oxidant. The nozzle 60 may be built in the combustor body 51 to prevent damage to the combustor housing 50 due to thrust force. The nozzle 60 is connected to one end of the solid fuel 10 via the first gasket 15. At this time, the oxidant supply unit 40 is connected to the other end of the solid fuel 10 via the second gasket 16.

As shown in FIG. 2, the nozzle 60 has a shrinking cone portion 61 which is narrow in the traveling direction of the driving force from the solid fuel 10 side, and a width of the nozzle 60 is along the traveling direction of the driving force from the shrinking cone portion 61. The widening cone portion 62 is formed to penetrate through. Then, the flame or heat passing through the solid fuel 10 is compressed while passing through the shrinking cone portion 61 and is discharged to the expansion cone portion 62, so that propulsion force can be amplified. The inlet of the nozzle 60 is composed of an inlet of the shrinking cone portion 61 facing the solid fuel 10, and the outlet of the nozzle 60 is formed of the end of the expansion cone portion 62.

The nozzle support jaw portion 63 for coupling the first gasket 15 may be provided at the edge of the nozzle 60 at the suction port side of the nozzle 60. The nozzle support jaw 63 may be recessed at the edge of the nozzle 60.

A nozzle closing jaw portion 64 may protrude from the discharge port edge of the nozzle 60 (the edge of the extension cone portion 62) at the discharge port side of the nozzle 60. The nozzle closing jaw portion 64 protrudes in a ring shape from the end edge of the expansion cone portion 62. The nozzle dead end portion 64 may be inserted into the pressure discharge hole 521 to suppress or prevent the flow of the nozzle 60 in the combustor housing 50. In addition, the nozzle closing jaw portion 64 may protrude to the outside of the combustor housing 50 in a state in which the nozzle closing jaw portion 64 is inserted into the pressure discharge hole 521. The nozzle dead end portion 64 may shield the flame or heat discharged through the nozzle 60 and the combustor housing 50.

The rocket housing 70 forms the exterior of the rocket device. Combustion housing 50 is coupled to the rocket housing 70.

The rocket housing 70 includes a rocket body 71 into which the combustor housing 50 is inserted and supported, a nose cone 72 provided at an end of the propagation direction of the rocket body 71 due to the propulsion force, and a circumference of the rocket body 71. It may include a wing 73 provided in.

When the combustor housing 50 is inserted and supported in the rocket body 71, the second closing cap 53 may be exposed to the outside as shown in FIG. 1.

The dummy unit 80 is embedded in the rocket housing 70 to support the combustor housing 50. The dummy unit 80 may include an injection unit for injection of the parachute and the parachute.

According to the rupture-type rocket device described above, the oxidant supply unit 40 can be controlled only by the control of the ignition unit 20, thereby controlling the transfer of the oxidant between the oxidant capsule 30 and the solid fuel 10. Can be.

In addition, the present invention, in controlling the transfer of the oxidant between the oxidant capsule 30 and the solid fuel 10, can replace the function of the valve provided in the oxidant supply unit 40, the valve and the control of the valve Since the necessary additional components are omitted, it is possible to reduce the load and size of the rocket system, simplify the control operation for combustion of the solid fuel 10, and relatively improve the propulsion of the rocket device in response to the reduced load and size. .

In addition, the present invention can increase the retraction rate, improve the propulsion performance, and increase the combustion efficiency through the swirl flow according to the combustion in the solid fuel (10).

In addition, the present invention facilitates the manufacture and coupling of the ignition unit 20, it is possible to stabilize the coupling of the ignition unit 20 and the solid fuel (10).

In addition, the present invention can be stored separately of the oxidant capsule 30, simplify the inlet opening of the oxidant capsule 30 in the process of assembling the oxidant capsule 30 in the robot device, it is possible to prevent the leakage of the oxidant. .

In addition, the present invention implements the modularization of the rocket device through the combustor housing 50, as well as the individual components are closely coupled to each other through a modular rocket device, while realizing a combustion phenomenon similar to the actual rocket, water rocket or air Like a rocket, you can secure it.

In addition, the present invention can prevent the flow of components in the combustor housing 50 through the gaskets, and can improve the adhesion between the components.

In addition, the present invention can amplify the driving force through the nozzle 60, and shields between the discharged combustion material and the combustor housing 50, and can improve the coupling force between the nozzle 60 and the combustor housing 50. have.

In addition, the present invention can stabilize the flight of the rocket housing 70 through the rocket housing 70.

In addition, the present invention stabilizes the laminated coupling of the rupture member 42 and the piercing 43 and the sealing ring 44 in the supply body 41, and the arrangement and coupling between the supply body 41 and the oxidant capsule 30 For simplicity, it is possible to facilitate the exact position of the oxidant capsule 30 in the supply body (41).

In addition, the present invention facilitates the breakage of the breaking member 34 by the coupling force between the supply body 41 and the oxidant capsule 30, facilitates the opening of the inlet 32 of the oxidant capsule 30, and prevents leakage of the oxidant. You can prevent it.

In addition, the present invention prevents deformation and breakage due to direct contact with the oxidant through the rupture member 42, and can sufficiently withstand the pressure of the oxidant discharged from the inlet 32 of the oxidant capsule 30.

In addition, the present invention may have a mechanical strength that exceeds the discharge pressure of the oxidizing agent changes according to the external temperature through the rupture member 42.

In addition, the present invention, since the solid fuel 10 and the oxidant are stored separately after assembling the rocket device, there is no risk of explosion to ensure high safety, and the combustion phenomenon and the internal structure can be simulated or similar to the actual rocket. have.

In addition, the present invention is because the fumes and operation sounds generated during combustion are similar to the flight phenomena of the actual rocket, it is possible to use in everyday life, such as learning materials for educational field, props for leisure activities, and various applications Can be represented.

In addition, the present invention can be utilized as an optimal educational rocket model or leisure rocket model through the best safety.

Although the preferred embodiments of the present invention have been described with reference to the drawings as described above, those skilled in the art can variously change the present invention without departing from the spirit and scope of the present invention as set forth in the claims below. Can be modified or changed.

10: solid fuel 11: propulsion hole 12: first supporting jaw
13: second supporting jaw portion 14: ignition unit seating portion 15: first gasket
16: 2nd gasket 20: ignition unit 21: ignition agent body
22: igniter 23: ignition line 30: oxidant capsule
31: injection portion 32: inlet 33: capsule portion
34: breaking member 35: support gasket 40: oxidant supply unit
41: supply body 411: seating hole 412: cardboard jaw
413: exposed hole 42: rupture member 421: curvature
422: engaging portion 43: piercing 431: piercing plate portion
432: communication hole 433: communication tube 44: sealing ring
50: combustor housing 51: combustor body 52: first closing cap
521: pressure discharge hole 53: the second closing cap 54: capsule pressure member
60: nozzle 61: shrinking cone portion 62: expansion cone portion
63: nozzle support jaw 64: nozzle dead jaw 70: rocket housing
71: Rocketbody 72: Nozcon 73: Wings
80: dummy unit

Claims (8)

In the oxidant supply unit for connecting the oxidant capsule and the solid fuel in which the oxidant is stored so that the oxidant is supplied to the solid fuel,
The oxidant supply unit,
A supply body formed through the exposed hole forming the discharge path of the oxidant and disposed between the oxidant capsule and the solid fuel;
A rupture member that blocks the oxidant from being delivered to the solid fuel and closes the exposed hole so as to be decomposable by flame or heat; And
And a piercing hole portion formed through the communication hole portion corresponding to the exposed hole portion to form a discharge path of the oxidant, and laminated to the rupture member so as to face the oxidant capsule.
The bursting member,
And a curvature having a groove having an inner cross section having an arc shape.
The minimum thickness (mm) of the curvature is referred to as t,
The pressure MPa of the oxidant acting on the curvature is referred to as P,
Internal diameter (mm) of the curvature is referred to as D,
The ellipsoidal shape coefficient of the curvature is referred to as A,
When the yield stress MPa of the curvature is S,

An oxidant supply unit for a rocket device, characterized in that a phosphorus relation is established. The method of claim 1,
The supply body,
A seating hole portion into which the injection portion of the oxidant capsule is inserted; And
An oxidant supply unit for a rocket device, comprising: a cardboard jaw portion provided in the seating hole to seat the rupture member. The method of claim 1,
The piercing is,
A piercing plate portion formed through the communication hole portion and laminated on the rupture member; And
And a hollow communication tube part protruding from the piercing plate part so as to communicate with the communication hole part. In the burst member provided in the oxidant supply unit for supporting the oxidant capsule in which the oxidant is stored,
The bursting member,
Prevent the oxidant from being delivered to the solid fuel and decompose by flame or heat;
The bursting member,
And a curvature having a groove having an inner cross section having an arc shape.
The minimum thickness (mm) of the curvature is referred to as t,
The pressure MPa of the oxidant acting on the curvature is referred to as P,
Internal diameter (mm) of the curvature is referred to as D,
The ellipsoidal shape coefficient of the curvature is referred to as A,
When the yield stress MPa of the curvature is S,

A rupture member of the oxidant supply unit, characterized in that the phosphorus relation is established. delete delete The method of claim 4, wherein
The bursting member is a bursting member of the oxidant supply unit, characterized in that it comprises a celluloid material. The method of claim 4, wherein
The bursting member,
Ignition (ignition) temperature of at least 200 degrees Celsius;
Mechanical strength to withstand pressures up to 1000 psi at 100 degrees Fahrenheit; And
Rate of decomposition of 2 mm / s or more upon decomposition by flame or heat;
Burst member of the oxidant supply unit, characterized in that to satisfy at least one of the.

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